Flying missiles



H. PH. ca. A. R. VON ZBOROWSKl 2,957,416

FLYING MISSILES Oct. 25, 1960 a Sheets-Shed 1 Original Filed April 14, 1952 INVEN TOR flimur 1 /1 GAR ww zaowawsm' BY QW W H. PH. G. A. R. VON ZBOROWSKI FLYING MISSILES 3 Sheets-Sheet 2 Original Filed April 14, 1952 INVENTOR MEL/war P6. Von fio'RoWS/(i BY I Add? TTORNYfl Oct. 25, 1960 H. PH. G. A. R. VON ZBOROWSKI 2,957,416

FLYING MISSILES 3 Sheets-Sheet 5 Original Filed April 14, 1952 NVE N TOR //L/VUT 7 /7. 6/25? VON ZBOPOWSK 2,957,416 FLYING MISSILES te ate ,0

Helmut Ph. G. A. R. von Zborowski, Chateau de Bonssy St.-Antoine par Brunoy, France Apr. 14, 1952, Ser. No. 282,107. application July 13, 1956, Ser. No.

2 Claims. (Cl. 102-50) The present invention relates to flying missiles comprising a body the surface of which is one of revolution about the longitudinal axis of symmetry of the missile, this surface constituting substantially the whole lift producing surface of the missile.

The object of my invention is to provide a missile of this kind which is better adapted to meet the requirements of practice than those known up to this time, in particular concerning the stability and range of its trajectory.

For this purpose, according to my invention, I provide such a missile with a trimming spoiler projecting from a surface of the missile in a plane transverse to the longitudinal axis thereof, the center of area of the projecting portion of the spoiler being eccentric with respect to said longitudinal axis, said spoiler being mounted to turn about said longitudinal axis, and pendulum means are operatively connected to the spoiler to maintain its center of area in a predetermined radial position in space with respect to said longitudinal axis, such positiou'being chosen to give the missile a positive angle of incidence.

It should be well understood that, in the following description and claims, the term spoiler designates an aerodynamic control device capable, when projecting from an aerodynamic surface, of changing the airflow along said surface with respect to what it would be if said spoiler did not project therefrom, with the object of controlling the angle of incidence of said surface with respect to its trajectory.

Preferred embodiments of my invention will be hereinafter described with reference to the accompanying drawings, given merely by way of example, and in which:

Fig. 1 is a diagrammatic elevational view of a rotary flying missible provided with a trimming spoiler accord ing to my invention;

Fig. 2 illustrates the path of travel of such a missile;

Figs. 3 and 4 are respectively a front view and a sec tional view on the line IV--IV of Fig. 3 of the spoiler mounting means of the missile illustrated by Fig. 1;

Fig. 5 shows a modification of the missile of Fig. 1;

Fig. 6 is a front view corresponding to Fig. 5;

Figs. 7 and 8 are views similar to those of Figs. 5 and 6, relating to another modification;

Figs. 9 and 10 are, respectively, an elevational view of a rotary missile provided with control means of another type but still according to my invention and a front view of said control means; 7

Figs. 11 to 14 inclusive show four different constructions of rotary missiles provided with control means according to my invention;

Figs. 15, 16 and 17 are partial sectional views of three different retractable control means according to my invention.

It is known that one way of increasing the range of a flying missile, either self-propelled or not, the theoretical trajectory of which is shown by curve C int Fig' 2, consists in giving the lift producing surface of the missile a positive incidence with respect to its trajectory by means 2,957,416 Patented Oct. 25, 1960 ice of suitable trimming means, the true trajectory of such a missile, for the same initial velocity, being then shown by curve C which is flatter and gives a longer range than curve C.

On the other hand, it is advantageous to make use of missiles rotating about. their longitudinal axis of symmetry because the deflections from the desired path of travel of the missile which are due to unavoidable imperfections in the symmetry of the missile take place alternately in one direction and the opposite one in the course of the rotation of said missile and therefore balance one another.

But it will be readily understood that when the missile is caused to rotate about its longitudinal axis, or is allowed to rotate freely about this axis, it becomes very diflicult to give a positive lift angle to its aerodynamic system. Conventional trimmings as above referred to can no longer be used because, in the course of the rotation of the missile, they would pass through position where, instead of imparting the desired positive lift angle to the aerodynamic system of the missile, they would contribute in deviating said missile from its desired path.

The object of the present invention is to overcome this ditficulty. V

In the construction of Fig. l, the flying missile essentially includes a body 1 and a coaxial tail annular wing 1a constituting the only lift producing surfaces of the missile. The desired position angle of incidence is given to the missile by a spoiler 2, which acts by modifying the flow of air along the annular wing.

According to my invention, as illustrated in detail. by Figs. 3 and 4, this spoiler 2 is carried by a piece 3 rotatable with respect to annular wing 1a about the axis thereof, whereby the axis of symmetry of spoiler 2 (and therefore the radial plane in which is located the aerodynamic reaction it produces) can assume any position about the longitudinal axis of the missile. This piece 3 is provided with a counterweight 4, so as to form a pendulum pivoted on wing 1a about the axis thereof. Wing 1a is provided with an annular slot 5 to accommodate spoiler 2.

With such an arrangement, spoiler 2 will remain suit= ably disposed to give annular wing 1a the desiredpositive angle of incidence despite rotation thereof about its longitudinal axis.

Preferably, an anti-friction bearing 6, for instance a ball bearing, is provided between rotatable member 3 and wing structure 1a, in order to eliminate any risk of said rotatable member being driven in the rotation movement of'wing structure 1a.

Inthe construction of Fig. l, spoiler 2 projects from the wing structure outwardly at the upper part thereof and near the trailing edge thereof. Fig. 5 shows another construction in which spoiler 2 projects from the wing structure inwardly at the upper part thereof and near the leading edge.

In this case, advantageously, as shown by Fig. 6, ball bearing 6 is interposed between rotatable piece 3' and the outer wall of wing 1a, whereas, in the construction of Figs. 3 "and 4, ball bearing 6 is interposed between rotatable piece 3 and the inner wall of wing 1a.

In the construction of Fig. 7, spoiler 2 projects inwardly' from the lower portion of annular wing 1a and is located close to the trailing edge of said wing.

Fig. 8 shows the respective elements of the arrangement of Fig. 7. The ball bearing 6 is interposed between piece 3 and the outer wall of annular wing in. Spoiler 2 and counterweight 4 are, in this construction, located on the same side of the axis of the annular wing, while, in the above described constructions, they were diametral- 1y opposed.

Figs. 9 to 11 show how the invention may be applied to flying missiles in which the spoilers are located ahead of the main annular wing.

In the construction of Fig. 9, the missile is provided, at the front thereof, with an auxiliary annular Wing 1b and spoiler 2 projects outwardly, at the lower pant thereof and near its trailing edge.

In the construction of Fig. 11, spoiler 2 is mounted on a streamlined part extending ahead of annular wing 1a.

In both of these cases piece 3 which supports ranged as shown by Fig. 4 being located both on axis of the missile.

The missiles shown up tions corresponding to Figs. 12 to 14 show missile 1 in which the this missile including, portion Id.

In the construction (Figs. 9 and 11), the rotating the spoiler is, for instance, ar-

10, spoiler 2 and counterweight the same side of the longitudinal to now included aerofoil secsubsonic velocities.

constructions of a rotary flying air speed velocity is supersonic, at the front thereof, a pointed of Fig. 12, spoiler 2 is mounted at the rear and at the upper part of the body 1 of the missile. In the construction of Fig. 13, it is mounted at the front and at the lower part of body 1. In the construction of Fig. 14, it is mounted at the lower part of the pointed portion 1 In all the embodiments of my invention above described, the spoiler means constantly project from the surface of the wing structure. Now, this is unconvenient in practice because said means may be deteriorated during transportation, storing and launching of the missile.

According to a feature of are made retractable.

For instance, the spoiler may be mounted retractable, as shown by Fig. 15, the base thereof being guided between two plates 11 carried by rotatable piece 3, and a spring 10 urging said spoiler outwardly.

According to another construction, illustrated by Fig. 16, which corresponds to a construction as shown by Fig. 4, the whole of rotatable piece 3 and the bearing 3a on which it is mounted (i.e. the inner race of ball bearing 6) can be moved with respect to wing structure 1a so as to retract spoiler 2 inside this wing structure. For this purpose, this inner race 3a is slidable transversely in a guide ring 18 rigid with wing structure 1a. Springs 12 urge this ball bearing inner race 3a toward coaxial position with respect to annular wing structure 1a, where spoiler 2 projects from said wing structure. To retract this spoiler, it sufl'lces to push the whole of parts 2-3-3a downwardly against the action of springs 12.

Advantageously, means are provided for temporarily holding spoiler 2 in retracted position, said means being preferably adapted to release said spoiler, so that it returns into active position, in response to the effect of the acceleration imparted to the missile when it is launched.

Such means are shown by Fig. 17, which illustrates a construction analogous to that above described with reference to Fig. 16. They include a lever 14 pivoted at 15 to the wing structure In and the hooked end 13 of which engages a projection of spoiler 2 to keep it in retracted position. A spring 17 tends to keep lever 14 in the spoiler holding position shown by the drawing. A weight 16 is provided at the lower end of lever 14 so that, under the effect of the launc 'ng acceleration imparted to the missile, this weight lags behind .by inertia and disengages hook 13 from spoiler 2, thus enabling spring 12 to return part 3a into coaxial relation with the annular wing, thus moving spoiler 2 to the outside.

Such a holding device might be used with the construction of Fig. 17.

my invention, said spoilers In the above description, my invention has been more especially described as applied to rotating flying missiles having an annular wing. However it is applicable to all kinds of flying missiles, for instance to rockets, even provided with a stabilizing tail unit, having propelling means which act for only a portion of their trajectory, and also to projectiles sent from a gun or the like and which may be self-propelled along a portion of their trajectory.

In a general manner, While I have, in the above description, disclosed what I deem to be practical and efiicient embodiments of my invention, it should be well understood that I do not wish to be limited thereto as there might be changes made in the arrangement, disposition and form of the parts without departing from the principle of the present invention as comprehended within the scope of the accompanying claims.

The present application is a division of my U.S. patent application Ser. No. 282,107, filed April 14, 1952, now abandoned.

What I claim is:

1. A flying missile which comprises, in combination, a body the surface of which is one of revolution about a longitudinal axis of symmetry, this surface constituting substantially the whole lift producing surface of the missile, a single trimming spoiler device projecting from a surface of the missile in a plane transverse to said longitudinal axis, the center of area of the projecting portion of said spoiler device being eccentric with respect to said longitudinal axis and at a constant distance therefrom, the area of said projecting portion being constant, means mounting said spoiler device to turn freely with respect to said body about said longitudinal axis through 360", and gravity pendulum means olfset from said longitudinal axis operatively connected to said spoiler device and rotatable about said longitudinal axis to maintain the center of area of said spoiler device in a predetermined radial position in space with respect to said longitudinal axis, such position being chosen to give the missile a positive angle of incidence.

2. A flying missile which comprises, in combination, a body the surface of which is one of revolution about a longitudinal axis of symmetry, this surface constituting substantially the whole lift producing surface of the missile, a ring mounted in said body in a plane transverse to said longitudinal axis to turn freely with respect to said body about said axis through 360, a single trimming spoiler carried by said ring projecting from a surface of the missile in a plane transverse to said longitudinal axis and at a constant distance therefrom, the area of said projecting portion being constant, the center of area of the projecting portion of said spoiler being eccentric with respect to said longitudinal axis, and gravity pendulum means offset from said longitudinal axis carried by said ring and rotatable therewith about said longitudinal axis to position the center of area of said spoiler device in a predetermined radial position in space with respect to said longitudinal axis, such position being chosen to give the missile a positive angle of incidence.

References Cited in the file of this patent UNITED STATES PATENTS 1,043,074 Davis Nov. 5, 1912 1,166,879 Alord Ian. 4, 1916 1,300,708 Edison Apr. 15, 1919 1,940,387 Boykow Dec. 19, 1933 2,402,718 Albree June 25, 1946 2,520,433 Robinson Aug. 29, 1950 2,584,826 Wyckoff Feb. 5, 1952 FOREIGN PATENTS 797,933 France Feb. 24, 1936 

